Optimizing Asteroid Orbit Insertion with Electric Propulsion

This paper presents a significant advancement in the design of low-thrust electric propulsion missions. By developing a multidisciplinary design optimization (MDO) framework, the authors address the limitations of traditional approaches that rely on simplifying assumptions about thrust and specific impulse. The framework's ability to simultaneously optimize the trajectory and power system, while explicitly coupling electric propulsion performance to time-varying solar power availability and solar array degradation, represents a key innovation. The use of a high-fidelity variable-specific impulse model of the SPT-140 Hall thruster further enhances the realism of the simulations. The demonstration of the framework through an orbit insertion scenario around asteroid 16-Psyche highlights its practical applicability. The results of the simulations demonstrate the importance of integrated power optimization for realistic electric propulsion mission design. However, the framework's complexity may limit its applicability to simpler mission designs. The accuracy of the model also depends on the fidelity of the SPT-140 Hall thruster data. Future research should focus on extending the framework to incorporate in-situ resource utilization (ISRU) for propellant production. This would further enhance the efficiency and sustainability of deep-space missions. The framework could also be adapted for other types of electric propulsion systems, such as gridded ion thrusters or magnetoplasmadynamic thrusters. Finally, the framework could be integrated with other mission design tools to provide a more comprehensive solution for planning deep-space exploration missions.

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